Aileron for fixed wing aircraft

ABSTRACT

An aircraft aileron system ( 10, 10 ) is comprised of two panels ( 12, 14, 28, 30, 62, 70 ) located at the rear portion of the wing (W 24, 54 ), in a spanwise direction and aligned with the wing&#39;s trailing edge. The panels are independently hinged at their leading edges and rotate to make angular deflections with respect to the wing. The upper, aileron panel ( 12, 30, 62 ) is restricted to upward deflection only from its neutral position and in operation is deployed independently as an aileron. The lower, auxiliary flap panel ( 14, 28, 70 ) is capable of both upward and downward deflections from its neutral position, and is deployed independently downward as an auxiliary flap. Both panels are deployed together upwardly only as an aileron. Alternatively, the auxiliary flap panel is capable of downward deployment only, to provide a simpler aileron system. For roll control of an aircraft during cruise, the aileron panel on one side only is deflected up while the aileron panel on the other side remains in its neutral position.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to aircraft flight control devices, andmore particularly to wing-mounted control devices. More specifically,the invention relates to an improved aileron system especially suitablefor fixed-wing aircraft which provides a flight control system havingimproved efficiency and versatility.

2. Related Art

Immediately obvious with the invention of the airplane was theimportance of controlling movement in flight, as an uncontrollableairborne airplane will soon crash. Aviators soon settled on ailerons forroll control. An aileron is a hinged panel on the trailing edge of thewing, usually located at the outboard portion of the wing, which, whendeflected downwardly, increases the lift of that wing, to roll or bankthe airplane into a turn. At the same time, the aileron on the otherwing is deflected upwardly, to decrease the lift on that wing and thusaugment the rolling motion. The configuration and application of theconventional aileron system has changed little, if at all, over morethan nine decades since the first fixed-wing aircraft were produced.

One of the most objectionable features of conventional aileronapplication is a phenomenon known as “adverse yaw,” and virtually allexisting fixed-wing aircraft suffer disadvantageous consequencesassociated with adverse yaw. When a turn is initiated with conventionalailerons, the nose of the airplane turns first in a direction oppositeto that of the intended turn. This is usually compensated by usingrudder deflection to “coordinate” the turn. The adverse yawing motion isa direct result of aileron application. While producing more lift tobank the airplane into a turn, the downwardly-deflected aileron alsoproduces more drag, which acts momentarily to cause the airplane's noseto turn in the direction opposite to the intended turn. That is, whenone wing is lifted relative to the other wing by operation of aconventional aileron to bank the airplane into a turn, it is also pulledback away from the turn relative to the wing on the other side, causingthe nose initially to turn, or yaw, in the direction opposite to theturn. This effect becomes increasingly detrimental as the roll rateincreases and/or airspeed decreases.

Adverse yaw produced by the conventional aileron contributes to spinentry. Instinctive application of conventional ailerons during attemptedspin recovery merely aggravates the spin condition. When spinning, anairplane is descending and turning in a tight spiral flight path. Theconventional aileron is not effective in spin recovery. In a left handspin, for instance, the left wing is down and toward the center of thespiral. Instinctively, many pilots are tempted to initiate right stickor control yoke movement to roll towards the right and out of the spin.With conventional ailerons this will deploy the left aileron down andthe right aileron up. The left aileron will create more drag than theform drag caused by the up-going right aileron and the spin will befurther aggravated. For an airplane equipped with conventional aileronsapplication of rudder alone is used for spin recovery. Much of spintraining involves conditioning pilots to avoid the instinctive attemptto roll out of the spin. Nonetheless, many pilots have aggravated spinsby attempting such recoveries with conventional ailerons.

Various methods and devices have been used to counter adverse yaw. Amongthem are the differential aileron with its finite deflection ratio, andthe spoiler. The differential variation of conventional ailerons is themost commonly used solution and provides some marginal improvement, buthas limitations. Use of spoilers may obviate adverse yaw, but spoilerspresent their own problems. Spoilers are so named because they spoil oreffectively eliminate lift. Ailerons deliver continuously variablechanges in lift within their operational envelopes, whereas spoilersoperate in a stepwise manner, being functionally either on or off, andthus are difficult to modulate between full and zero effect. Rollcontrol is difficult to achieve with spoilers without complicatedsub-systems or augmenting devices.

Another disadvantage of conventional ailerons is that they also requirecommitment of a sizable portion of the trailing edge of the wing thatcould otherwise be used for beneficial high-lift devices. Such devicesallow lower approach, landing and takeoff speeds, especiallyadvantageous for heavy, high-speed commercial and high-performancemilitary aircraft.

There are several prior-art devices which, at first glance, may appearvery similar to the present invention. On closer examination, however,none of them yields the stated results or functional capabilities ofthis invention. Most of the previously employed devices are designed andapplied as drag devices, such as ground control spoilers, drag rudders,dive brakes, or nominal flaps.

Examples of devices known in the art which are deployed upwardly toprovide aircraft control may be found in the following U.S. patents:

1,504,663 Wright Aug. 12, 1924 2,136,845 Fenton Nov. 15, 1938 2,138,326Pouit Nov. 29, 1938 2,152,974 Riviere April 4, 1939 2,158,092 Taylor May16, 1939 2,254,304 Miller Sept. 2, 1941 2,407,401 Clauser et al. Sept.10, 1946 2,791,385 Johnson May 7, 1957 3,120,935 Perrin Feb. 11, 19644,717,097 Sepstrup Jan. 5, 1988

Pouit describes a flap which acts more like a present-day spoiler, toprevent aircraft capsizing. In a variation, the flap has separate upperand lower elements, of which the upper element is simply hinged, and canbe extended upwardly only by the upper deflection of the lower, actuatedelement. The upper flap member is not capable of movement independent ofthe lower member. Both wing flaps are operated together. Perrindescribes a glider control system wherein the aileron has a secondaryaileron which can be extended up to act as a drag rudder for directionalyaw control in place of a rudder.

Fenton relates to a device which is basically a flap with small,subsidiary flaps on the upper and lower trailing edges. The subsidiaryflaps are moved up or down through fixed, predetermined displacement, tocontrol aircraft roll movement, with the deployment of the subsidiaryflap on each side of the aircraft controlled such that when thesubsidiary flap on one side is up, the corresponding subsidiary flap onthe other side is down. Due to their small size, the effectiveness ofthe subsidiary flaps is doubtful.

Clauser et al. provide a lateral control arrangement having an airfoilmember pivoted near the tip of the wing which functions as an aileronand a flap, or an “ailerflap,” and a second airfoil member, or a “slotlip,” pivoted above the ailerflap. Each element can pivot up and downabout its neutral position. The slot lip regulates the slot spacingbetween the wing's trailing edge and the leading edge of the ailerflap,to alter the lift provided by the ailerflap during takeoff and landing.During flight, lateral control is achieved with the ailerflaps operatedconventionally as ailerons. The slot lips move in unison with theailerflaps, and are not capable of independent upward movement.

Johnson relates to a landing control system having a spoiler locatedabove a conventional flap. The downwardly extending flap is used toaugment lift, and the upwardly extending spoiler act as a drag plateduring landing approach. The flap and spoiler on both wings are actuatedsimultaneously.

Miller provides a split aileron which is a combination aileron and flap.Each wing has an aileron extending almost the full span, and a flappivoted beneath the aileron. The aileron functions conventionally, andsize of the flap is limited to that of the aileron. Wright et al.describes a split flap arrangement wherein a lower element pivots downas a flap and an upper element, which pivots up and down, serves as anaileron. Riviere, Taylor and Sepstrup disclose split aileronarrangements.

Other examples of control surfaces which are formed of two, separatelyhinged sections and can be deployed together up and down as conventionalflaps or ailerons, and are also capable of separating from each other toprovide flap and air brake functions, are described in U.S. Pat. Nos.2,427,980, 2,445,833, 2,612,329 and 2,582,348.

More recently flaperons have been employed which function both as flapsand ailerons, and offer pseudo-full-span flaps. They, however, greatlycompromise the roll function and produce even greater adverse yaw thanthe conventional aileron when roll function is needed. Spoilers attemptto achieve objectives similar to those of the present invention, but ata great compromise in flight characteristics. Spoilers tend to have deadbands and are difficult to modulate. They, after all, “spoil” ratherthan modulate lift. Roll control systems involving spoilers have beenused on aircraft with mixed results.

The conventional differential aileron used on most existing aircraftlessens but does not eliminate adverse yaw. It occupies a sizableportion of the wing's trailing edge, thus preventing the installation offull-span flaps. With some aircraft designs, high roll rates have beensought with the use of full-span ailerons, thus obviating entirely theinstallation of flaps. Other aircraft designs have sacrificed aileronsfor full-span flaps, necessitating the inefficient use of tail planes orwing spoilers for roll control. No other flight control devices have theversatility or efficiency of the present invention. The Frise aileronalso claims to lessen adverse yaw by deliberately creating more drag onthe upwardly-deflecting aileron. This device also does not allowinstallation of a full-span flap.

The device closest in construction and function to the present aileronsystem was invented by the inventors of the present invention. Presentedas the “Delta aileron” which was placed on top of a one-piece full-spanflap, it has some of the features of this invention. But, it is notaerodynamically as efficient and offers less functional capability thanthe present invention. For example, it does not have an auxiliary flapand in its present form cannot be used as a drag rudder.

SUMMARY OF THE INVENTION

The aileron system of the present invention simultaneously eliminatesall the above problems while offering desirable features not possessedby conventional ailerons. Accordingly, an object of the invention is toprovide an aileron system which is simple in design and construction,and more importantly, in its unique method of deployment and thefunctional results obtained. Other objects of the invention are toprovide an aileron system of the foregoing type which: eliminatesadverse yaw associated with previous aileron roll control systems;provides benefits in spin avoidance and spin recovery; can be deployedfor flight path control, air braking and as a drag plate; results in awing which is cleaner, with fewer actuating mechanisms, and isaerodynamically efficient and correct in operation; allows for theincorporation of full-span flaps and other high-lift devices on thetrailing edge of a wing; and provides an overall aircraft control systemwhich is simpler in construction and requires fewer components, is lessexpensive, reduces maintenance requirements, reduces weight, andprovides the aircraft with lower takeoff and landing speed capabilities,with the advantages attendant therewith.

The present invention is basically used for roll control of fixed-wingaircraft around the longitudinal axis. It is a combination ofaerodynamic control surfaces which deflect upwardly only when deployedfor roll control. By operating these surfaces judiciously and inconjunction with their counterparts on the other wing, and the flapsystems, many favorable results may be obtained for the control ofaircraft.

The aileron system of the present invention is similar in shape andexternal appearance to the conventional aileron, but its constructionand deployment are entirely different. It is comprised of two panelslocated at the rear portion of the wing, in a spanwise direction andaligned with the wing's trailing edge. The panels may be independentlyhinged at their leading edges or may be hinged on a common axis androtate to make angular deflections with respect to the wing. The upperor aileron panel is deflected upwardly only from the neutral position,while the lower, auxiliary flap is capable of both upward and downwarddeflections from the neutral position. The upper panel is deployedindependently as an aileron and the lower panel is deployedindependently as an auxiliary flap. Both panels are deployed togetherupwardly only as an aileron.

For roll control of an aircraft during cruise, the aileron panel on oneside only is deflected up while the aileron panel on the other sideremains in its neutral position. The auxiliary flap panel is arranged tomove with the aileron panel as a unit, such that the two surfaces forman “aileron” in the usual sense. To roll left, for example, the aileronof the present invention on the left wing is deflected up, while theaileron on the right wing remains in the neutral position. Theupwardly-deflected left aileron results in a negative change in thewing's lift coefficient, decreasing the lift on the left wing relativeto that of the right wing, and producing a roll to the left. Effectivelyjoining the upper and lower panels to move as a unit preserves thesmooth contour of the airfoil. In the deflected mode it is theequivalent of an airfoil with a reflex camber. Aerodynamically this is amuch more efficient “aileron” than that achieved by deflecting only theupper panel upwardly.

During flap deployment, the lower auxiliary flap panel is disengagedfrom the upper aileron panel, and operated to move with the main wingflaps to form a full-span flap. The upper aileron panel is then movedindependently to provide roll control. Only the auxiliary flap panel isarranged to move in conjunction with the aileron in the roll controlmode. The panel used as a dedicated flap is unaffected.

For use on small, general aviation aircraft, a simpler version of theaileron system may be utilized to facilitate construction and minimizeweight. The auxiliary flap panel may be left to function completelyindependently of the aileron panel. Its stowed position would be theneutral position, and it would move downwards only as a flap. Theauxiliary flap panel would not accompany the aileron panel in its upwardexcursions.

The aileron system of the present invention is placed at the trailingedge of the wing in much the same location as a conventional aileron.However, the inventive aileron is deflected upwardly only. As with otherailerons, deflection results effectively in a change of the airfoil'scamber and thus a change in the lift coefficient, C_(L). In the case ofthe present invention, the upward deflection of the aileron results in anegative change in C_(L). The wing deploying the present aileron thenproduces less lift than the other wing with its inventive aileronmaintained in the neutral position. Thus, the wing drops and theaircraft is rolled toward the lowered wing into a turn. Theupwardly-deflected inventive aileron protrudes into the stream of airflowing over the wing, creating form drag, to rotate the nose of theaircraft toward the turn. Unlike activation of conventional ailerons,this action produces favorable yaw.

The present invention's functional property of favorable yaw aids inboth spin avoidance and spin recovery. For an airplane using the presentaileron system, the same stick movement used by a pilot to roll rightand out of the left hand spin described above, results in only the rightaileron going up and on the outside of the spiral. The outward yawingmotion plus the outside wing being depressed will roll the airplane awayfrom the spiral center and aid in recovering from the spin. This willaugment the opposite rudder input usually used for spin recovery. Theform drag associated with the present invention also aids in spinrecovery. Depending on the installation, this effect may be accentuatedby the simultaneous deployment of the auxiliary flap panel with theaileron panel, creating a drag rudder on one wing, in this example theright wing.

Favorable yaw also ameliorates the difficulties associated withasymmetric loss of power during flight in multi-engine aircraft. Theminimum controllable airspeed, V_(mca), will decrease with use of thepresent invention, as will the required rudder authority and size, whileaircraft performance will increase.

Since it deflects upwardly only, the aileron system of the presentinvention frees up the entire wing's trailing edge for installation ofhigh lift or drag devices to lower approach, landing and takeoff speeds.With lower approach and landing speeds, aircraft, particularly heavycommercial or high performance military aircraft, may gain access toshorter runways. Carrier-borne aircraft may have slower, saferapproaches. These aircraft will have lower requirements for groundbraking and the maintenance of such systems. Additionally, the inventionmay be deployed symmetrically on both wings for flight path control, orsymmetrically in concert with flaps to function as air brakes or dragrudders.

The present invention is a simple system. It results in aircraft controlsystems and overall operations that are safer, more efficient andaerodynamically correct, simpler and more economical to produce andmaintain. It lends itself to systems of lighter weight, with the weightsavings being traded for increased fuel, cargo or passenger capacity, orsimply a lighter-weight aircraft.

Other objects and features and additional advantages of the inventionwill be apparent from the foregoing and the following description anddiscussion, in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIGS. 1A-1C each shows an airfoil section with the aileron system of thepresent invention, in different operational modes.

FIG. 1D shows an airfoil section with an alternate embodiment of theaileron system of the present invention.

FIGS. 1E-1G show different operational modes of the embodiment of FIG.1D.

FIG. 2 is a perspective view of a general aviation type aircraft withwings incorporating the aileron system of the present invention,executing a banking turn to the left.

FIGS. 2A and 2B each is a cross section of the wing, along view lines2A—2A and 2B—2B, respectively, in FIG. 2, showing the position of theaileron during the turn.

FIG. 3 is a perspective view of a wing showing the main and aileronauxiliary flaps deployed to form a full-span flap and the upper aileronpanel of the present invention in the neutral position.

FIG. 3A is a cross section of the wing along view line 3A—3A in FIG. 3.

FIG. 4 is a perspective view of a wing showing the main flaps in theirneutral positions and the aileron system of the present inventiondeflected up for flight path control.

FIG. 4A is a cross section of the wing along view line 4A—4A in FIG. 4.

FIG. 4B is a view similar to FIG. 4, but showing the auxiliary flaps ofthe aileron system in their neutral positions.

FIG. 4C is a cross section along view line 4C—4C in FIG. 4B.

FIG. 5 is a perspective view showing a wing with full-span flapsdeployed and the upper aileron panels of the present invention deflectedup simultaneously for air braking.

FIG. 5A is a cross section of the wing along view line 5A—5A in FIG. 5.

FIG. 5B is a view similar to FIG. 5 showing the aileron system of thepresent invention deployed as a drag rudder.

FIGS. 5C-5D are cross sections along view lines 5C—5C and 5D—5D,respectively, in FIG. 5B.

FIG. 6 is a schematic showing an embodiment of a system for operatingthe aileron system of the present invention.

FIG. 6A shows, to a larger scale, parts of the operating systemillustrated in FIG. 6.

FIGS. 7A-7C each shows a cross section of the wing along view line 7—7in FIG. 6, schematically illustrating different deployment modes of theaileron system of the present invention.

FIG. 8 is a plan view of a typical commercial jet aircraft wing withvarious flaps and aileron arrangements.

FIG. 9 is a wing cross section along view line 9—9 in FIG. 8, with anembodiment of the present invention incorporating a two-sectioned Fowlerflap in the stowed position.

FIG. 10 shows a portion of the operating subsystem for the Fowler flapshown in FIG. 9.

FIGS. 11A-11C each is a view of the wing shown in FIG. 9, depicting thecontrol surfaces in different stages of operation.

FIG. 12 shows schematically an embodiment of the present invention witha single-section Fowler flap.

FIG. 13 shows schematically an embodiment of the present invention witha split flap.

FIG. 14 is a plan view of the present aileron system for a swept wingaircraft, schematically illustrating some components of the operatingmechanism.

FIG. 15 shows, to a larger scale, additional details of the operatingmechanism illustrated in FIG. 14.

FIG. 16 is a view along view line 16—16 in FIG. 15.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

FIGS. 1A, 1B and 1C each shows a cross section, or an airfoil section,of a wing W incorporating the improved aileron system 10 of the presentinvention, illustrating different stages in the deployment of thesystem. The aileron system 10 is shown to include an upper, aileronpanel 12 and an auxiliary flap panel 14 stowed underneath the aileronpanel. Both the aileron panel 12 and the auxiliary flap panel 14 areseparately hinged to the wing's rear spar 16 or other hard points, andcan be operated independently, but can also be made to operate in unisonfor certain functions when they are engaged. In FIG. 1A, both panels areshown in their respective neutral or retracted positions, in which theyform smooth continuations of the respective upper and lower surfaces ofthe wing W. With the aileron panel 12 deflected upwardly, as shown inFIG. 1B, the auxiliary flap panel 14 also is made to deflect upwardly toform an aerodynamically efficient “aileron” in the usual sense. With theauxiliary flap panel 14 deployed downwardly, as shown in FIG. 1C, theaileron panel 12 can remain in the neutral position (shown in solidlines) or be deflected up only, as indicated by the broken line 17.

Instead of separately hinging the auxiliary flap panel and the aileronpanel, these panels may be hinged to rotate about a common axis, asshown in FIG. 1D. In this configuration as well, the aileron panel 12can be deflected upwardly (FIGS. 1E and 1G), but is not deflecteddownwardly beyond its neutral position (FIG. 1F), whereas the auxiliaryflap panel 14 can be deflected upwardly in unison with the aileron paneland down independent of the aileron panel.

For small, general aviation aircraft, a simplified version of theaileron system illustrated in FIGS. 1A-1C may be utilized to facilitateconstruction and minimize weight. The auxiliary flap panel may be leftcompletely independent of the aileron panel. Its retracted or stowedposition would be the neutral position, as shown by the auxiliary flappanel in FIG. 1A, and it would move downwards only as a flap, such asshown by the auxiliary flap panel in FIG. 1C. However, the auxiliaryflap panel would not move with the aileron in its upward excursions.

In the following description, the term “aileron” will refer to both theaileron panel and the auxiliary flap panel when they are operated tomove as a unit. The term “aileron panel” will refer to the upper panelwhen it functions as an upwardly-movable only aileron, independently ofthe auxiliary flap panel. Similarly, the term “auxiliary flap panel”will refer to the lower panel when it functions as a flap, independentlyof the aileron panel.

In FIG. 2, a general aviation type aircraft 18 is depicted making a leftbanking turn by rotating about the aircraft's longitudinal axis L. Inthis maneuver, the aileron on the left wing or left aileron 20 isdeflected up while the right aileron 22 remains in its neutral position,as shown respectively by the wing cross section depicted in FIGS. 2A and2B. The angular deflection required for a banked turn is comparable tothat of a conventional aileron. The rate of roll can be modulated byvarying the deflection angle. This illustrates the basic roll controlfunction of the present invention in which no adverse yaw or rotationabout the vertical axis Y is produced. On the contrary, favorable yawresults. With conventional ailerons, this same maneuver would beachieved by simultaneously deflecting the left aileron up and the rightaileron down, resulting in the adverse yaw discuss above. In the presentinvention, the aileron panel is not deflected downwardly beyond itsneutral position.

Each of the ailerons 20 and 22 can be modulated independently to deflectto any degree in order to provide the roll rate desired, or be deflectedsimultaneously for flight path control or air brakes, including theextreme case of maximum upward deflection of both for ground control,for landing roll-out. Wing panels conventionally deployed for the lattermode are usually referred to as ground control spoilers. The inventorsconsider “spoiler”, a term which originated in the glider or sail planecommunity, a misnomer for panels used in this mode as brakes. A spoileris an aerodynamic obstruction positioned on top of the wing,perpendicular to the air stream, at approximately the mid-point of thewing chord. When deployed, a spoiler creates highly turbulent flow overthe top of the wing and actually destroys, or “spoils” the wing's lift,thus the name spoiler. When the lift is spoiled, the weight of the wingexceeds the lift supporting it and causes the wing to drop.

The ground control “spoiler” is an aerodynamic drag device primarily. Itdoes create turbulence, mostly behind the wing. This drag panel actseffectively as a flap mounted and deployed on the upper surface of thewing, and instead of creating lift as a conventional flap on the wing'sbottom, this panel behaves as a negative flap creating a downward force,or negative lift, which is beneficial in applying more force on theaircraft's landing gear to permit harder wheel braking. This is donebest when the lower, auxiliary flap panel is retracted once the airplaneis on the ground. If the upper drag panel and the lower flap panel aredeployed at the same time the forces tend to negate each other. Underthis circumstance the drag force of both panels are still in effect andbecome an air brake. It can become a drag rudder if only one wing'scontrol surfaces are deployed in this manner.

The present aileron system can be used for different modes of the flightregime. FIG. 3 shows a general aviation type wing 24, such as the wingshown in FIG. 2, with full-span flaps formed by the main flap 26 and theauxiliary flap 28 deployed together. Both the main flap 26 and theauxiliary flap 28 are shown in FIG. 3 at maximum deflection. In thismode the aileron panels 30 can remain stowed in the neutral position(FIG. 3A) or each can be deflected up individually for roll control. Theailerons 10′ can be deflected upwards on both sides simultaneously toprovide modulated flight path control when the main flaps 26 areretracted, as shown in FIGS. 4 and 4A. The auxiliary flap panel 28 movesupwardly with the aileron panel 30 in this case. An alternate method isto deflect upwards only the aileron panels 30, with the auxiliary flappanels remaining in their neutral positions, as shown in FIGS. 4B and4C.

FIG. 5 depicts the control surfaces of the aileron system 10′ deployedin the air brake mode. Actually, the air brake can be deployed in twoways. The first method is in conjunction with the full-span flaps, e.g.,in preparation for landing, as shown in FIG. 5. When further reductionof airspeed is required, the aileron panels 30 can be deflected upsimultaneously and symmetrically on both wings to form the air brake.The aileron panels continue to provide roll control by thesuperimposition of individual and independent further upward deflection.The second method is during level, or cruise, flight when a decrease inairspeed is desired. Both aileron panels 30 can be deflected up and bothauxiliary flaps 28 deflected down to form an air brake. Note FIGS. 5 and5A. A variation of the second method can be attained by deploying theaileron panel 30 and the auxiliary flap panel 28 together on one wingonly, with the corresponding control surfaces on the other wingremaining retracted or in their respective neutral position, to form adrag rudder as shown in FIGS. 5B, 5C and 5D. The drag rudder, as thename implies, performs the same function as the tail rudder, bydragging, or yawing one wing to the direction desired.

FIG. 6 schematically depicts a general aviation type wing 24 with anexample of an operating system to implement control of the ailerons. Acable or tubing linkage 32 is connected between a control stick 34 and acam/pulley arrangement 36 coupled to a push rod linkage 38 to actuatethe aileron 10′. As shown in FIGS. 6 and 6A, the auxiliary flap panel 28can be actuated by a cockpit lever 40 connected by another cable or tubelinkage 42 to transfer bell cranks 44 and 46 (shown in schematic form),which in turn actuate linkage 50 to move the auxiliary flap 28 up ordown on command from the pilot. The push rod 48 is biased by a spring49. Other mechanisms may perform the same functions by transducing thepilots actions through any means of control input, such as conventionalstick or yoke movement, or pressure sensing device, or even neuralimpulse or electro-encephalographic interpretation, with physicalimplementation by any electrical, mechanical, hydraulic or other motiveforce.

Operation of the controls can be seen by referring to FIGS. 6, 6A and7A-7C. The aileron panel 30 and the auxiliary flap panel 28 are shown intheir respective neutral position in FIG. 7A, and FIG. 7B shows theaileron 10′ deflected up. With the auxiliary flap panel 28 not deployedin the flap mode, the auxiliary flap's control cable 42 is allowed tounload, and push rod 48 will engage transfer bell crank 46 to move asecond push rod 50, which in turn moves the auxiliary flap panel up inconcert with the aileron panel 30. In FIG. 7C, the aileron panel 30 isin the neutral position and the auxiliary flap panel 28 is deflecteddown. When the auxiliary flap lever 40 is actuated in the cockpit viathe cable 42, tension will rotate transfer bell crank 44, to move pushrod 48 sideways to disengage from transfer bell crank 46. Note that theauxiliary flap lever and the main flap lever can be combined. With theauxiliary flap panel 28 disengaged, the aileron panel 30 is free forindependent deployment up, modulated for aileron roll function up to aposition indicated by line 52 or modulated flight path control up tomaximum deflection indicated at 53 for ground control drag panelfunctions.

Cable or tubing arrangements comprise very simple control systemscommonly found on small, light aircraft. They are by no means the onlysystems capable of performing the functions described, and are chosenonly as examples. The controls can be actuated by any means capable oftransducing a pilot's actions, including but not limited to conventionalstick or control yoke and rudder, flight directors or other automated orcomputerized pilots, fly-by-wire or even voice command or neuralimpulse. Control actuation may be implemented via cables, tubings,pushrods, or electric servo motors, electromagnetic actuators, hydrauliccylinders, pneumatic systems, or any method of transferring force tocause mechanical movement of the aileron and flaps.

For high performance aircraft, particularly heavy commercial or militaryaircraft, the number of possible configurations of the ailerons andflaps may be very large. Such complex configurations and deploymentschedules might be best managed by pilot control commands implementedthrough a computer.

A plan view of a commercial jet aircraft wing 54 is shown in FIG. 8,with leading edge Krueger flaps 56, 57, 58, and 59. The inboard aileron60 and the outboard aileron 62 line the wing's trailing edge. The brokenlines indicate the extended position of a two-section Fowler flap 64 and66 which form the auxiliary flap panel for the ailerons 60 and 62,respectively, and the extended position of the main Fowler flap 68. Thefull-span flap system can be comprised entirely of two-section Fowlerflaps. That is, the lower auxiliary flap panel can be a Fowler flap. Theaileron panel may extend from section 62 to section 60, with the aileronpanel of the inboard section 60 being deployed as a flight path controland ground control drag panel only. In this application the auxiliaryflap panel need not follow the aileron panel's upward movement, since inthis particular application its function is to create drag. Anycombination of flap types can be used for the main and the lowerauxiliary flap panel of the aileron system as desired to suit theengineering, production, or performance objectives of individualapplications.

FIG. 9 shows in schematic form an embodiment of the aileron system 62 inwhich the lower auxiliary flap 66 is a two-section Fowler flap havingsections 70 and 71. The broken lines indicate the upward deployedposition of the aileron 62. An example of a suitable guide for theauxiliary flap panel 66 comprised of the Fowler flap is shown in FIG.10, wherein a track 72 guides the deployment of the two-section Fowlerflap. Track 72 is disposed in a fairing located on the wing, at the endsof the flaps, such as fairings 74 visible in FIG. 8. These Fowler flapsections are shown in the stowed positions as 70 and 71 and in themaximum extended positions as 70′ and 71′. The larger of the Fowler flapsections 70 rides on a shuttle 76, shown in FIG. 11A, which is guidedalong the track 72. Flap deployment is accomplished byelectrically-driven screw jacks 78, which are attached to the shuttle76. Rotation of the screw effects a rearward push on the screw jack 78to extend the larger of the Fowler flap sections 70, which in turn pullsout the smaller section of the Fowler flap 71 via a connecting linkage80 (FIG. 10.) A hydraulic cylinder 82 actuates the auxiliary flap, whichis the larger of the two Fowler flap sections, through a transfer barlever 83.

The aileron system is shown in the up deflected position in FIG. 11B.The auxiliary flap 70 is hinged at the front end to the shuttle 76, andthe rear part of the flap is lifted away from the shuttle. When theauxiliary flap 70 is in the fully retracted position (FIG. 11A) it isautomatically released mechanically from the shuttle 76. When theauxiliary flap is ready for extension, electric microswitches (notshown) will signal the screw jack motor circuits (not shown) that theauxiliary flap is stowed in its neutral position. At that time the screwjack motor will begin operating. A mechanical device on the shuttle willautomatically lock the flap to the shuttle and begin its deploymentalong the track. The broken lines 84 and 85 indicate the aileron paneland the auxiliary flap panel are in one of the air brake mode positions.

The fully deployed auxiliary Fowler flap is illustrated in FIG. 11C,which depicts the relationship between the two sections of the Fowlerflaps. The aileron panel 62 can be operated independently in thissituation, from its stowed neutral position (solid lines) to anintermediate upward deflection (phantom lines) and further to amaximally deflected position indicated by the line 84.

A schematic drawing is presented in FIG. 12, to illustrate an alternateform of flap that may be utilized with the aileron system 62. In thisembodiment a single-section Fowler flap 86 is shown. Phantom lines showthe deployed position of the auxiliary panel (Fowler flap) 86 and theaileron panel 62. The broken line 84 indicates the position of theaileron panel 62 in its functional mode as a ground control drag panel.The single-section Fowler flap is less complicated, and requires asmaller track and other deployment mechanisms which can be contained ina smaller, more streamlined fairing. This results in a lighterstructure, etc.

In FIG. 13, a simple split flap arrangement is shown. The features ofthe present invention are still preserved. As above, this is a simplerconstruction but with a trade-off in efficiency and performance.

FIG. 14 is a schematic plan view showing the aileron system of theinvention 70 installed on a swept-wing jet aircraft. The operatingdevices used to control the aileron system are similar to thosedescribed with respect to FIGS. 10 and 11A-11C. The auxiliary flap 70 isretracted beneath the aileron (not shown), and each end of the flap issupported by a shuttle 76, which in turn rides on a track 72 guided byrollers 88. Hydraulic cylinders 81 and 82 actuate the movements of theaileron panel and the auxiliary flap panel separately. The extension andretraction of the shuttles are effected by a pair of electromechanicalscrew jacks 78. Additional details of the shuttle 76 are shown in FIGS.15 and 16. Two rollers 88 guide the shuttle 76 on the track 72. Theleading edge of the flap 70 is pivotally supported on the shuttle 76 bya hinge 90. Toward the rear of the flap, at about ⅓ of the flap chord, alocking mechanism is provided which includes a bolt 92 passing through astrong point bracket 94 attached to the flap structure, a spar, or someequivalent structure. A lever bar 98, hinged at 99 to the shuttle, canrotate back and forth (arrow A) to actuate the locking bolt 92 via alinkage 100. The lever bar 98 is attached to a screw jack 78, and adetent block 102 attached on a lever 104 with a roller tip 105, canrotate with an up and down motion, indicated by the arrow B. The rollertip 105 rides on a roller guide (not shown) which governs its movementto release the detent block 102 at the appropriate location.

The sequence of auxiliary flap extension begins with the screw jack 78being rotated to push back on the lever bar 98, which in turn pushes thelinkage 100 to lock the bolt 92 onto the bracket 94. Further movementcauses the shuttle 76 to move and extend the auxiliary flap 70, such asdepicted in FIGS. 11C and 12. At the same time the roller-tipped lever104 is guided to rotate upwardly, to place the detent block 102 betweenthe lever bar 98 and a shuttle step 106. The lever bar 98 is then lockedand prevented from rotating. The retraction sequence is the reverse ofthe above extension sequence. When the lower auxiliary flap panel 70 isfully retracted, the roller guide will rotate the roller-tipped lever104 downward, to extract the detent block 102. The lever bar 98 then canrotate forward to extract the bolt 92. The lower auxiliary flap panel 70then is unlocked from the shuttle 76, but hinged at the forward end andis free to rotate around this hinge point 90.

The operation of the aileron system, in conjunction with an aircraft'sconventional flap system to provide aircraft control can be betterunderstood from the following description of its operation through ahypothetical flight of an aircraft from takeoff to landing, for example,a large commercial jet aircraft. Typically, the pilot would select flapdeployment for takeoff. Here, both the main flap and the auxiliary flappanel beneath the aileron panel would be deflected downward from theirstowed, neutral positions. During and after the takeoff the upwardlydeflecting aileron panel would be deployed to maintain full andindependent roll control authority.

After gaining altitude and speed, the pilot would retract the flaps,with the auxiliary flap panel then moving to its stowed position whereit effectively becomes one with the aileron panel to form anaerodynamically efficient “aileron.” This integrated aileron willmaintain roll control during cruise flight with a drag efficientaileron. To roll the aircraft to the left, for example, the pilot wouldraise the left aileron. The right aileron would remain in its neutralposition. No adverse yaw would be experienced during this deployment,and the rolling motion would be modulated continuously by pilot controlinput.

For descent, the pilot might reduce power. With this invention, however,the power settings could be left unaltered, or the descent rateaugmented with the flight path control mode of the aileron system byraising the ailerons of both wings symmetrically. The aircraft coulddescend in this fashion with wings level, the degree of augmentation ofthe sink rate continuously modulated by the simultaneous deflection ofthe ailerons. Full roll control authority would be maintained bysuperimposing differential aileron deflection. During this maneuver theaircraft sinks or descends but remains in a level attitude or nearly so,the cabin floor likewise, a quality appreciated by flight attendants andpassengers. Airspeed could remain constant during descent even withthrottle settings little changed from cruise. On retraction of theailerons, the aircraft would stop its descent and resume its previouslevel flight path and airspeed. Steeper descent rates could be obtainedby symmetrical deployment of the drag rudders, that is, the aileron andauxiliary flap panels together, on both wings as air brakes. These airbrakes with their outboard location on the wing would not be limited indeployment, as are many conventional speed brakes with their inboardlocation, by turbulent air flow created for the tailplane to flythrough.

During approach to landing, the auxiliary and main flaps would bedeployed independently for small changes in wing camber, leading todeployment of both the main and auxiliary flaps together to producefull-span flaps for increased lift and/or drag at low speeds. Flapdeployment may be combined here with symmetrical deployment of theaileron panels as in the above-described flight path control mode toprovide an air braking function. Again, superimposing differentialaileron deployment would provide roll control.

On touchdown, the pilot would retract all flaps and raise the dragpanels and the aileron panels as additional drag panels. This actionwould place additional weight on the wheels for better ground contactthat would allow harder wheel braking and at the same time exertpressure (as a function of speed) to hold the aircraft on to the ground.

The invention also offers advantages in dealing with asymmetric thrustconditions or power loss, a scenario that drives much of multi-engineaircraft design and certification requirements. With asymmetric enginepower output, the aileron of this invention or the drag rudder functionwould provide directional control superior to that of current systems,with less compromise in aircraft performance and decreased need forrudder size and control authority. Asymmetric thrust, which occurs forexample when there is greater power output by the engine or engines onthe right side of an aircraft, or there is less power output by theengine or engines on the left side, will cause a yawing and turningmotion of the aircraft to the left, towards the side with less power.This is usually considered an emergent situation. This yawing motiontypically is counteracted with rudder input. The combination ofasymmetric thrust and compensatory rudder input will allow the aircraftto hold a linear course, but the aircraft now also will be sideslipping,or have a sideways component to its motion. This sideslip induces alarge amount of drag and may cause severe decrease in aircraftperformance at a time of greatly reduced power and aerodynamic controlauthority. This is counteracted by banking or rolling the wings towardthe side with more power. With conventional aileron control systems thiswill, as with normal flight situations, induce adverse yaw which willrequire even greater rudder deflection, with the demands on the ruddernow including compensation for both the asymmetric power condition aswell as the adverse yaw induced by banking the aircraft to eliminatesideslip.

An aircraft with conventional empennage equipped instead with thepresent invention would still require rudder input to counteract yawgenerated by the asymmetric thrust condition. But banking toward theside of greater thrust to compensate for sideslip would generatefavorable yaw, aiding the rudder rather than demanding even more rudderinput. The rudder then could be of smaller size, generating lessaerodynamic drag in all flight conditions, weighing less and costingless to produce and to maintain. Deployment of both the presentinvention and the rudder under these circumstances would induce lessdrag than conventional control surfaces, yielding greater aircraftperformance under these worrisome conditions.

Disclosed herein is a unique aileron system in conjunction with flaparrangements which offer multiple function with advantages over past andpresent systems for aircraft control. Among its many advantages, thepresent invention eliminates adverse yaw associated with previoussystems of aileron roll control. Spin entry involves the creation ofadverse yaw, usually at low flight speeds. The invention allowsairplanes to maneuver well-controlled at lower speeds and providesfavorable rather than adverse yaw, decreasing the likelihood of spinentry, improving safety. The present invention operates on the wing'supper surface only. The entire trailing edge is made available for highlift devices, e.g. flaps and other functionaries that deflect or movedownwards. Any sort of high lift or drag device that requires varyingthe wing trailing edge downwards can be implemented with use of theinvention. Full-span ailerons may be installed for higher roll ratesdesired for acrobatic or other aircraft demanding high maneuverability.

The present aileron system can be employed to deploy simultaneously onboth wings for flight path control. No rolling motion is caused bysymmetrical deployment. The equal deployment results in an equaldecrement of lift on both wings and a descending flight path with smallchanges in pitch attitude and power settings. This effect, as all otherswith the invention, can be modulated continuously in contrast to that ofmany conventional air or speed brakes. In this mode, control of theindividual ailerons provides roll control.

When the aileron system is used in concert with flaps, air brakingresults. Asynmmetric deployment results in “drag rudders” and selectiveleft or right yaw. With large deflection angles the aileron system maybe used as a “drag plate”, useful, for example, for braking on landingroll-out.

The invention offers many favorable economies. It is simple in designand construction. No new technologies are necessary for production. Itallows for full-span flaps, among other trailing edge devices. A typicalcommercial airliner could replace its dual conventional ailerons,multiple spoilers, complicated flap systems and all their attendantactuating systems with simply one aileron system of the presentinvention and one flap on each wing. Construction would be simpler andless expensive. Maintenance would involve fewer systems with feweropportunities for malfunction. The wing would be cleaner, fitted withfewer of the multiple protruding pods now present for actuating systems,and more aerodynamically efficient and correct in operation. The weightsaved could be traded for additional fuel, improving range, oradditional cargo or passengers, or simply result in a lighter airplanewith better performance. Lower takeoff and landing speeds impose lessstress on landing gear systems, as well as pilots, and allow aircraft touse smaller airfields. Utility is increased and safety enhanced.

Implementation of the invention control system does not result in anycompromise or negative trade-off in any aspect of aircraft performance.Neither is it more expensive to engineer or produce. To the contrary itresults in performance increases and economies in production andoperation under every consideration.

Although not specifically described herein or illustrated in thedrawings, it is understood that all of the elements described above arearranged and supported in an operative fashion to form a complete,operative system. Such complementary structure is known and would beprovided by a person skilled in the art. Numerous modifications andvariations of the present invention are possible in light of the abovedisclosure. It is therefore to be understood that within the scope ofthe invention defined in the appended claims the invention may bepracticed otherwise than as specifically described herein.

What is claimed is:
 1. An aerodynamic control system for roll control ofan aircraft around a longitudinal axis of the aircraft, the aerodynamiccontrol system comprising: a first wing having a rear portion, the firstwing having a top surface and a bottom surface; an aileron assemblyhaving an upper panel and a lower panel, the upper panel being pivotallyattached to the top surface of the first wing at the rear portion andthe lower panel being pivotally attached to the bottom surface of thefirst wing at the rear portion, wherein the upper panel and the lowerpanel are operatively related such that both the upper panel and thelower panel are deflected in an upward direction as a unit from both anupper panel neutral position and a lower panel neutral position, theupper panel having an upper surface where the upper surface of the upperpanel forms a continuation of the first wing top surface when the upperpanel is in the upper panel neutral position, wherein the upper panel islimited to deflect only upwardly relative to the upper panel neutralposition, the lower panel having a lower surface where the lower surfaceof the lower panel forms a continuation of the first wing bottom surfacewhen the lower panel is in the lower panel neutral position; and asecond wing, the second wing being opposite the first wing, the secondwing having the aileron assembly such that only the upward deflection ofthe upper panel of the aileron assembly on the second wing is sufficientto effect roll control of the aircraft without adverse yaw of a nose ofthe aircraft.
 2. An aerodynamic control system as set forth in claim 1,wherein the lower panel can move downwardly from the lower panel neutralposition, independently of the upper panel.
 3. An aerodynamic controlsystem as set forth in claim 1, wherein the roll control of the aircraftmay be effected without adverse yaw of the nose of the aircraft byupwardly deflecting only the upper panel of the aileron assembly of thefirst wing.
 4. An aerodynamic control system as set forth in claim 3,wherein the roll control of the aircraft may be effected without adverseyaw by only upwardly deflecting the upper panel and the lower panel ofthe aileron assembly of the first wing as a unit.
 5. An aerodynamiccontrol system for roll control of an aircraft around a longitudinalaxis of the aircraft, the aerodynamic control system comprising: a firstwing having a rear portion, the first wing including a top surface and abottom surface; an aileron assembly having an upper panel and a lowerpanel, the upper panel being pivotally attached to the top surface ofthe first wing at the rear portion and the lower panel being pivotallyattached to the bottom surface of the first wing at the rear portion,wherein the upper panel and the lower panel are operatively related suchthat both the upper panel and the lower panel arc deflected in an upwarddirection as a unit from both an upper panel neutral position and alower panel neutral position, the upper panel having an upper surfacewhere the upper surface of the upper panel forms a continuation of thefirst wing top surface when the upper panel is in the upper panelneutral position, wherein the upper panel is limited to deflect onlyupwardly relative to the upper panel neutral position, the lower panelhaving at least one section, the lower panel having a lower surfacewhere the lower surface of the lower panel forms a continuation of thefirst wing bottom surface when the lower panel is in the lower panelneutral position; and a second wing, the second wing being opposite thefirst wing, the second wing having the aileron assembly such that onlythe upward deflection of the upper panel of the aileron assembly on thesecond wing is sufficient to effect roll control of the aircraft withoutadverse yaw of a nose of the aircraft, where the lower panel of both thefirst wing aileron assembly and the second wing aileron assembly can beextended rearwardly to increase an effective wing area and can bedeflected in a downward direction from the lower panel neutral position,independently of the upper panel, to provide flap function for theaircraft.
 6. An aerodynamic control system for roll control of anaircraft around a longitudinal axis of the aircraft, the aerodynamiccontrol system comprising: a first wing having a rear portion, the firstwing having a top surface and a bottom surface; an aileron assemblyhaving an upper panel and a lower panel where the upper panel ispivotally attached to the top surface of the first wing at the rearportion and the lower panel is pivotally attached to the bottom surfaceof the first wing at the rear portion, wherein the upper panel and thelower panel are operatively related such that both the upper panel andthe lower panel are deflected in an upward direction as a unit from bothan upper panel neutral position and a lower panel neutral position, theupper panel having an upper surface where the upper surface of the upperpanel forms a continuation of the first wing top surface when the upperpanel is in the upper panel neutral position, wherein the upper panel islimited to deflect only upwardly relative to the upper panel neutralposition, the lower panel having a lower surface where the lower surfaceof the lower panel forms a continuation of the first wing bottom surfacewhen the lower panel is in the lower panel neutral position; and asecond wing, the second wing being opposite the first wing, the secondwing having the aileron assembly such that only the upward deflection ofthe upper panel of the second wing aileron assembly is sufficient toeffect roll control of the aircraft without adverse yaw of a nose of theaircraft, where the upper panel of both the first wing aileron assemblyand the second wing aileron assembly are deflected up simultaneously tofunction as drag panels.
 7. An aileron system to control roll of anaircraft, the aileron system comprising: a first wing of the aircraft,the first wing including a rear portion; a second wing of the aircraft;an upper panel pivotally attached to the rear portion of the first wing,the upper panel having an upper surface that is flush with an uppersurface of the first wing when the upper panel is in an upper panelneutral position such that the upper panel forms a continuation of thefirst wing; and a lower panel pivotally attached to the rear portion ofthe first wing opposite the upper panel, wherein the first wing includesa lower surface which is flush with a lower surface of the lower panelwhen the lower panel is in a lower panel neutral position such that thelower panel forms a continuation of the first wing, the lower panelincluding a section where a lower surface of the section of the lowerpanel is flush with the lower surface of the first wing when the lowerpanel is in the lower panel neutral position such that the section ofthe lower panel forms a continuation of the first wing, the upper paneland the lower panel being operatively related such that both the upperpanel and the lower panel are deflected in an upward direction as a unitfrom both the upper panel neutral position and the lower panel neutralposition.
 8. An aileron system as recited in claim 7, wherein the lowerpanel moves in a downward direction from the lower panel neutralposition independently of the upper panel to provide flap function forthe aircraft.
 9. An aileron system as recited in claim 8, wherein thesection of the lower panel further includes a plurality of sectionswhere the plurality of sections move in the downward direction as thelower panel moves in the downward direction.
 10. An aileron system asrecited in claim 9, wherein the upper panel is deflected in the upwarddirection to function as a drag panel.
 11. A method for controllingmovement of an aircraft with an aileron system, the aircraft having afirst wing and a second wing opposite the first wing where both thefirst wing and the second wing have a rear portion, the aileron systemincludes a first plurality of aileron panels pivotally attached to therear portion of the first wing and the aileron system includes a secondplurality of aileron panels attached to the rear portion of the secondwing, the method comprising: deflecting a first upper aileron panel ofthe first plurality of the aileron panels into a deflected position;controlling a first lower panel of the first plurality of the aileronpanels where the first lower panel is independently operable from thefirst upper aileron panel such that the first lower panel deflects withthe first upper aileron panel; and maintaining a second upper aileronpanel of the second plurality of the aileron panels in an upper panelneutral position such that an upper surface of the second upper aileronpanel is substantially flush with an upper surface of the second wing toform a continuation of the upper surface of the second wing in the upperpanel neutral position.
 12. A method for controlling movement of anaircraft with an aileron system as recited in claim 11, the methodfurther comprising: positioning the first upper aileron panel in theupper panel neutral position from the deflected position such that anupper surface of the first upper aileron panel is substantially flushwith an upper surface of the first wing to form a continuation of theupper surface of the first wing.
 13. A method for controlling movementof an aircraft with an aileron system as recited in claim 12, the methodfurther comprising: positioning a second upper aileron panel of thesecond plurality of aileron panels in the upper panel neutral positionsuch that an upper surface of the second upper aileron panel issubstantially flush with an upper surface of the second wing to form acontinuation of the upper surface of the second wing.
 14. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 13, the method further comprising: positioning the first aileronpanel of the first plurality of the aileron panels in a lower panelneutral position such that a lower surface of the first aileron panel issubstantially flush with a lower surface of the first wing to formcontinuation of the lower surface of the first wing.
 15. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 14, the method further comprising: positioning a second lowerpanel of the second plurality of the aileron panels in the lower panelneutral position such that a lower surface of the second lower panel issubstantially flush with a lower surface of the second wing to form acontinuation of the lower surface of the second wing.
 16. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 15, wherein the first upper aileron panel and the first lowerpanel are operatively coupled to move as a unit from the upper panelneutral position and the lower panel neutral position.
 17. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 16, wherein the second upper aileron panel and the second lowerpanel are operatively coupled to move as a unit from the upper panelneutral position and the lower panel neutral position.
 18. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 17, the method further comprising: moving the first lower panel ina downward direction independent of the first upper aileron panel.
 19. Amethod for controlling movement of an aircraft with an aileron system asrecited in claim 18, the method further comprising: moving the secondlower panel in a downward direction independent of the second upperaileron panel.
 20. A method for controlling movement of an aircraft withan aileron system as recited in claim 19, the method further comprising:moving the first upper aileron panel and the second upper aileron panelin an upward direction from the upper panel neutral position to modulateflight path control.
 21. A method for controlling movement of anaircraft with an aileron system as recited in claim 20, the methodfurther comprising: moving the first upper aileron panel in the upwarddirection; moving the first lower panel in the downward direction;maintaining the second upper aileron panel in the upper neutralposition; and maintaining the second lower panel in the lower panelneutral position to form a drag rudder.
 22. A method for controllingmovement of an aircraft with an aileron system as recited in claim 21,the method further comprising: deflecting the first plurality of aileronpanels in the upward direction to function as drag panels for theaircraft.
 23. A method for controlling movement of an aircraft with anaileron system as recited in claim 22, wherein the first lower panel andthe second lower panel function as auxiliary flaps.
 24. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 23, the method further comprising: deflecting the first upperaileron panel and the second upper aileron panel in the upwarddirection; and deflecting the first lower panel and the second aileronpanel in the downward direction to form an airbrake.
 25. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 24, the method further comprising: deflecting the first upperaileron panel in the upward direction; and maintaining the second upperaileron panel in the upper neutral position in order to control roll ofthe aircraft.
 26. A method for controlling movement of an aircraft withan aileron system as recited in claim 19, wherein the upper panel andthe lower panel form a trailing edge of the wing.
 27. A method forcontrolling movement of an aircraft with an aileron system as recited inclaim 19, the method further comprising: reflexing the wing trailingedge by moving both the first aileron assembly and the second aileronassembly in an upward direction, thereby reducing drag of the aircraft.28. An aerodynamic control system for roll control of an aircraft arounda longitudinal axis of the aircraft, the aerodynamic control systemcomprising: a wing having a rear portion, the wing having a top surfaceand a bottom surface; and an aileron assembly having an upper panel anda lower panel, the upper panel being pivotally attached to the topsurface of the wing at the rear portion and the lower panel beingpivotally attached to the bottom surface of the wing at the rear portionwherein the upper panel and the lower panel are operatively related suchthat both the upper panel and the lower panel are deflected in an upwarddirection as a unit from both an upper panel neutral position and alower panel neutral position, the upper panel having an upper surfacewhere the upper surface of the upper panel forms a continuation of thewing top surface when the upper panel is in the upper panel neutralposition, the upper panel being limited to deflect only upwardlyrelative to the upper panel neutral position.
 29. An aerodynamic controlsystem for roll control of an aircraft around a longitudinal axis of theaircraft, the aerodynamic control system comprising: a wing having arear portion, the wing including a top surface and a bottom surface; andan aileron assembly having an upper panel and a lower panel, the upperpanel being pivotally attached to the top surface of the wing at therear portion and the lower panel being pivotally attached to the bottomsurface of the wing at the rear portion, wherein the upper panel and thelower panel are operatively related such that both the upper panel andthe lower panel are deflected in an upward direction as a unit from bothan upper panel neutral position aid a lower panel neutral position, theupper panel having an upper surface where the upper surface of the upperpanel forms a continuation of the wing top surface when the upper panelis in the upper panel neutral position, wherein the upper panel islimited to deflect only upwardly relative to the upper panel neutralposition, the lower panel having a lower surface where the lower surfaceof the lower panel forms a continuation of the wing bottom surface whenthe lower panel is in the lower panel neutral position.
 30. Anaerodynamic control system for roll control of an aircraft around alongitudinal axis of the aircraft, the aerodynamic control systemcomprising: a first wing, the first wing including a top surface and abottom surface; an aileron assembly having an upper panel and a lowerpanel, the lower panel having a section, the upper panel being pivotallyattached to the top surface of the first wing, the lower panel beingpivotally attached to the bottom surface of the first wing, the upperpanel being limited to deflect only upwardly relative to an upper panelneutral position, the lower panel having a lower surface where the lowersurface of the lower panel forms a continuation of the first wing bottomsurface when the lower panel is in a lower panel neutral position,wherein the roll control of the aircraft may be effected without adverseyaw of the nose of the aircraft by upwardly deflecting only the upperpanel of the aileron assembly of the first wing; and a second wing, thesecond wing having the aileron assembly wherein the upper panel of theaileron assembly on the second wing remains in the upper panel neutralposition during upward deflection of the upper panel of the aileronassembly of the first wing.
 31. An aerodynamic control system as recitedin claim 30, the upper panel further comprising: an upper surface wherethe upper surface of the upper panel forms a continuation of the wingtop surface when the upper panel is in the upper panel neutral position.